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Sub Menu: GENESIS - Aircraft Design Details
IntroductionMultipurpose Landing GearTelescopic WingInterconnected Propeller Drive
Modular FuselageSimplicity of OperationAerodynamicsDesign Verification
SpecificationsComparison to the CompetitionSafetyReliability
MarketFrequently Asked QuestionsConclusionPatents

Design Verification
Gevers Aircraft, Inc. * GENESIS *

Latest technology analysis and verification.

Stability Verification:
Small TunnelThe static and dynamic stability of the design has been verified using a computer simulation based on an extensive wind tunnel study done by the United States Air Force and McDonnell Douglas Corp. This study, called the USAF Stability and Control Datcom (DATa COMpendium), is a four volume (3,000 pages) summary of wind tunnel tests performed for the purpose of providing stability derivatives and aerodynamic forces for analytical modeling of aircraft.

Over a period of three years a unique computer program was written which uses the DATCOM results for the sole purpose of verifying and optimizing the stability of the Genesis design. Other aircraft were modeled as a check of the accuracy of the program.

This study shows that the Genesis design has desirable characteristics in all measures of stability and control in both the wings retracted, and extended configurations, and with the gear in all positions. The controllability with an engine inoperative is a particularly significant improvement over conventional designs. The structurally efficient swept "T" tail shows excellent rudder control down through stall speed - no VMC speed. Rudder induced roll coupling is minimal.

Performance Verification:
The performance figures were verified using computer programs based on standard analytical methods found in widely used design texts. The accuracy of these programs were checked by modelling common production aircraft and verifying the performance data.

Wind Tunnel:
A medium sized wind tunnel was built (see the May 1994 issue of the EAA Experimenter Magazine) as an aid to flow visualization in the early stages of the design. In particular interactions between fuselage, wings, propeller arms, gear legs, and swept tail were of interest.

The tunnel is an open circuit (non-recirculating) type, 26 feet long overall and powered by a 200 HP internal combustion engine. The laminar velocity profile across the 19 inch high by 27 inch wide test section is exceptionally consistent.

Finite Element Model:
Many aspects of the design are being simulated using a finite element analysis computer program. This analysis is more sophisticated and complete than was used on the current general aviation light aircraft at the time they were designed.

Flying Model:
A 1/5th scale flying model was built and flown to verify specific aerodynamic considerations (primarily low speed rudder effectiveness) and to visualize component interactions.

The flying model, wind tunnel tests, and various computer programs are in agreement and are the basis for the preliminary performance figures.


GENESIS SECTION SUB MENU: Introduction.. Multipurpose Landing Gear.. Telescopic Wing.. Interconnected Propeller Drive.. Modular Fuselage.. Simplicity of Operation.. Aerodynamics.. Design Verification.. Specifications.. Comparison to the Competition.. Safety.. Reliability.. Market.. Frequently Asked Questions.. Conclusion.. Patents

Contact Gevers Aircraft by e-mail at <mgevers@iquest.net>